CN104246637B - Analyze the flying quality of aircraft record with the method being truncated to mission phase - Google Patents
Analyze the flying quality of aircraft record with the method being truncated to mission phase Download PDFInfo
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- CN104246637B CN104246637B CN201380018475.7A CN201380018475A CN104246637B CN 104246637 B CN104246637 B CN 104246637B CN 201380018475 A CN201380018475 A CN 201380018475A CN 104246637 B CN104246637 B CN 104246637B
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0243—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults model based detection method, e.g. first-principles knowledge model
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Abstract
The present invention relates to a kind of analysis method of the flying quality of record during the flight at least one times of aircraft, described flying quality includes the data of the characteristic parameter about described flight, said method comprising the steps of: determine the state model of flight, described state model includes some states, each state is corresponding to the possible mission phase of described aircraft, described state model includes conversion and at least one standard, described conversion is limited to the switching between the state that these are described, at least one standard described is used for init state pattern, described initialization standard is corresponding to the original state of described state model, each conversion and each initialization standard depend at least one characteristic parameter that can record during the flight of described aircraft.
Description
Technical field
The present invention relates to one group of flying quality of record during the flight at least one times of aircraft
Analyze.
Background technology
Regulation about maintenance and air traffic defines that airline is in order to ensure highest level
Client secure and the standard that has to comply with.
In order to optimize and monitor aerial operation, under the pressure of regulator, company is certainly
Oneself is equipped with the system for analyzing flying quality.
It is referred to as FDM (flying quality monitoring) or FPQA for analyzing the system of flying quality
(flight operation quality assurance).These systems include the flight data recorders equipping aircraft.
Such recorder e.g. black box, or special recorder, such as ACMS (fly
Row device condition monitoring system).
Using these systems, airline can come according to the conventional record of these flying quality values
Understanding flight course in detail, these conventional records are every time the flying of every airplane in airline
Record between the departure date.
For this purpose it is proposed, these systems detection during flying occur predefined event, then by
Expert analyzes the event of the technical failure that these instructions occur during flying, and it is flight journey
The circumstance or state of the unobserved prediction of sequence, thus in the possible breakdown being likely to occur or thing
Therefore commitment give a warning.
In order to apply this detection, each flight must intercept the data of record, and fly every time
Mission phase must be truncated to.
It practice, the detection of event was affected by the current flight stage.Such as, at aircraft
Take off period, when cruise time be not intended to same type of event.
Therefore, the intercepting of record data and the quality of intercept method ensure that the correlation of analysis.
The method analyzing flying quality including the flying quality intercepting record is known.
These known methods are based on the criterion setting the value about some flight parameter.This
A little methods are also based on typical case theory sequence.
Finally, this standard uses single source parameter.
Problematically, the standard used is (discontinuous or break bounds for misregistration
Value), the diversity for type of airplane, the diversity for flight operation or for produce
The X factor of the aerial operation of critical condition is unstable.
Summary of the invention
The present invention proposes to overcome at least one in these shortcomings.
For this purpose it is proposed, the present invention proposes a kind of analysis during the flight at least one times of aircraft
The method of the flying quality of record, described flying quality includes the characteristic parameter about described flight
Data, said method comprising the steps of: determine the state model of flight, described state mould
Formula includes some states, and each state is corresponding to the possible mission phase of described aircraft, described
State model includes conversion and at least one standard, and described conversion is limited to the shape that these are described
Change in state, at least one standard described is used for init state pattern, described initialization mark
The accurate original state corresponding to described state model, each conversion and each initialization standard depend on
In at least one characteristic parameter that can record during the flight of described aircraft.
The method according to the invention the most in turn comprises the following steps:
-extracting the flying quality recorded, described flying quality is joined about the feature of described aircraft
Number；
-calculate initialization standard according to the flying quality of the characteristic parameter about described aircraft,
During to detect original state initial that described flying quality starts corresponding described state model
Carve；
-count according to the flying quality about the characteristic parameter recorded after described initial time
Calculate multiple conversions of described state model, in order to detect the characteristic parameter about described aircraft
Flying quality starts the moment that the state of corresponding described state model changes；
-intercept described flying quality according to the moment thereby determined that, in order to by the flight number of record
Mate according to mission phase.
By following characteristics (individually using or with its most possible combination technically),
It is advantageously accomplished the present invention；
After the detection that the calculating of-described conversion is included in described original state described at least one
The calculating of the conversion of state model, it is given and forwards to corresponding to mission phase from described original state
The shape probability of state being referred to as current state.
The calculating of-described conversion includes at least one calculating changed, its be given from described currently
State forwards be later than the shape probability of state of described current state to.
-determine the time interval between two conversions, in order to determine that described flying quality is corresponding
The time period of the state of described state model.
The original state of-state model is the aircraft cruised or at the end of being in flight
Aircraft.
The calculating of-conversion includes flying according at least one characteristic parameter about described aircraft
Row data calculate criterion.
-eliminate the described flight before described flying quality starts the moment of corresponding original state
Data.
-described characteristic parameter is: normal acceleration, horizontal acceleration, longitudinal acceleration, height
Degree, the configuration of aileron, vertical speed and horizontal velocity, pressure altitude, radar altitude, rise and fall
The state of frame, course.
The state of described state model is: flight terminates, engine start, skid off, take off,
Refusal takes off, the second link, initial rise, rise, decline, cruise, march into the arena, go around,
Final approach, land, contact to earth and go around, slip into.
The invention still further relates to a kind of system for analyzing flying quality, including processing unit and depositing
Storage unit, described processing unit be applicable to application according to the method for aforementioned claim,
Described memory cell is used for storing state model.
The present invention has multiple benefit.
The intercepting of the data of record is automatic, and the Manual interception with the stage that flies will expend
Each flight at least five minutes.
It is sane for intercepting for misregistration.
The standard used is independent of the type of aircraft, this is because the parameter used is in institute
There is the general parameters all recorded on aircraft.
The accuracy intercepted have also been obtained further lifting.
Accompanying drawing explanation
According to explained below, other features, target and the advantage of the present invention will become obvious,
Explained below is pure signal and unrestricted, and should refer to appended accompanying drawing and read,
In the drawing:
-Fig. 1 shows the step of method according to the embodiment of the present invention；
-Fig. 2 shows state model according to the embodiment of the present invention；
-Fig. 3 shows the example of determination conversion according to the embodiment of the present invention.
Detailed description of the invention
Illustrating as mentioned by the introduction, flying quality is in the flight phase at least one times of aircraft
Between obtain record flight data.
These flying qualities are corresponding to the parameter of the aircraft of record.It can be speed, highly,
Position of aileron etc..
These record data are received, during its every a line is corresponding to flight with a matrix type
The record of aircraft parameters.
In order to flying quality is connected with mission phase, flying of each mission phase ground record
Row data are suitably intercepted.
Once they have been obtained intercepting, then they can be analyzed by they with relevant way.
Fig. 1 shows that use according to the embodiment of the present invention is same as analyzing the system of flying quality.
Such system includes memory cell 10, processing unit 20 and display unit 30, wherein processes
Unit 20 includes processor (not shown).
Memory cell 10 includes memory (not shown), is derived from aircraft for several times for storage
The flying quality of the record during flight.Such memory cell 10 can be by with hard disk or SSD
Or any other removable and rewritable storage bulking block (USB disk, memory card etc.) shape
Become.
Processing unit 20 can apply the method (seeing below literary composition) for realizing analyzing flying quality.
Memory cell 10 can be the ROM/RAM memory of processing unit 20, USB disk, memory
Card.Such processing unit is such as computer (multiple computer), processor (multiple places
Reason device), microcontroller (multiple microcontroller), microcomputer (multiple microcomputer),
Programmable logic controller (PLC) (multiple programmable logic controller (PLC)), special IC are (multiple
Special IC), other programmable circuits (multiple programmable circuit) or other include meter
The equipment of calculation machine, such as work station.
Display unit 30 can show the result of the method, the flying quality especially intercepted.This
The display unit of sample can be such as computer screen, monitor, flat screen, PDP display
The display device of any other type in curtain or known type.
About Fig. 2, describe the method for analyzing flying quality.
In first step 100, the state model (or state machine) of flight is determined.This
The determination of sample can be to be loaded in the memory cell 10 of analysis system by state model.
Fig. 3 shows a status that pattern.This state model be stored in especially Fig. 1 for
In the memory cell 10 of the system analyzing flying quality.
Such state model include some states E0, E0 ', E1, E2, E3, E4, E5,
E6、E7、E8、E9、E10、E11、E12、E13、E14、E15、E16。
Each state corresponds to the possible mission phase that aircraft is likely to be at during flying.
These mission phases are: flight terminates E0, engine start E1, skids off E2, takes off
E3, refusal take off E4, the second link E5, initial rise E6, rise E7, decline E8,
Cruise E0 ', the E10 that marches into the arena, the E9 that goes around, final approach E11, landing E12, contact to earth (the touch that goes around
And go) E14, slip into E15.
It is referred to document: commercial aviation secure group about the explanation of different mission phases, international
Civil aviation organization, " phase of flight definitions and usage notes ", in June, 2010.
State model include conversion, T1, T2, T3, T4, T5, T6, T7, T8, T9,
T10、T11、T12、T13、T14、T15、T16、T17、T18、T19、T20、T21、
T22, T23, T24, described conversion defines the switching between different conditions.
State model also includes that two initialize standard T0, T0 ', and it is corresponding at the beginning of state model
Beginning state E0, E0 '.
Both initialization standard T0, T0 ' are that two in state model may input.
Each conversion and each initialization standard depend on that at least one can flying at aircraft
The characteristic parameter of record between the departure date.
The characteristic parameter preferably parameter of conventional record in most aircraft.
These parameters are (Essential Terms used in aeronautics): turbine rotational speed (N2),
Engine fuel manifold 1, engine fuel manifold 2, EGT (EGT), normal acceleration,
Longitudinal acceleration, highly, the position of undercarriage, course, the speed on relative ground, aileron
Configuration, vertical speed, Mach number, pressure altitude, radar altitude.
In the range of one's duty analysis method, in second step 200, from the flying quality of record
Middle extraction is about the flying quality of the characteristic parameter of aircraft.These parameters are the most listed above.
In order to proceed the intercepting of flying quality, in step 300, initialization standard is calculated.
Specifically, by detection corresponding to the record at flying quality place of the original state of aircraft time
Carve.The original state of state model is " aircraft cruises " E0 ' or " aircraft is in and flies
Row terminates " E0.
This step 300 such as can eliminate the flying quality about imperfect flight, i.e. eliminates
Flying quality before the moment of flying quality correspondence original state.
Alternatively, it is also possible to analyze these data and think other purposes, this is because mission phase
May not be associated with these data.
It follows that in step 400, by according to the feature about record after initial time
The flying quality of parameter calculates some conversions of state model, in order to detection is about aircraft
The moment that the state of the flying quality corresponding states pattern of characteristic parameter changes.
In other words, once detect original state, the initial shape from this detection will be detected
In the possible conversion of state one.Then this stage being used for calculating conversion will be repeated, in order to place
Manage and whole effectively record the duration.
It should be noted that, the calculating of conversion includes according at least one characteristic parameter about aircraft
Flying quality calculate criterion.
Such as, if as it is shown on figure 3, from the beginning of state E0, conversion T5 being detected, then may be used
It is in the conclusion of state E2 obtaining aircraft.
Therefore, changed by detection, the state phase of flying quality corresponding states pattern can be speculated
Between time interval.
Therefore, according to transition detection, the conclusion that state changes can be obtained.
By using state model, can be to avoid exhaustive search.It practice, open from a state
Begin, the conversion of limited quantity only can be detected.
After detection conversion, exist in step 500, intercept flight according to the moment thereby determined that
Data, in order to make the flying quality of record corresponding to mission phase.
The method performs at each second of record.But, need some to join in higher frequency
Number, therefore the iteration of algorithm can use outside the execution step (1Hz) being positioned at program time
The parameter value carved.
As it has been described above, at least one characteristic parameter of aircraft is depended in conversion.
Conversion can depend on single features parameter.In this case, conversion is according to about this spy
The flying quality levying parameter calculates, and conversion afterwards is with threshold ratio relatively, in order to the most true
Determine whether conversion detected.
Conversion can depend on some characteristic parameters.In this case, join about these features
The flying quality of number processes, and is combined them and result is compared with threshold value,
To for example, determine whether conversion to be detected.
As calculating the example of situation of taking off, four parameters will be used: engine fuel manifold 1, with
Just momentum assembled by detection engine 1；Engine fuel manifold 2, in order to detection engine 2
Assembling momentum；The speed on ground relatively, in order to sense aircraft moves；And it is vertical
To acceleration, in order to sense aircraft is in boost phase.
While carrying out the calculating changed, first check for some parameters, and by weighted associations to often
Individual detection.
The parameter of detection is as follows:
If-about the parameter of engine fuel manifold 1 equal to particular value at least 3 seconds, then engine
1 is assembling momentum；
If-about the parameter of engine fuel manifold 1 equal to particular value at least 3 seconds, then engine
2 are assembling momentum；
If the speed on-relative ground is more than 5 nautical miles per hour, then aircraft moves；
If-longitudinal acceleration is more than 0.1g, then aircraft accelerates.
For each inspection, if meeting condition, relating value 1, if be unsatisfactory for, relating value zero.
In order to sense aircraft is taken off, if by four conditional add, obtaining at least 3
Value (meeting three in four conditions), then conversion will be detected.
Claims (10)
1. analyze the side of the flying quality of record during the flight at least one times of aircraft for one kind
Method, described flying quality includes the data of the characteristic parameter about described flight, described method bag
Include following steps:
-determining the state model (10) of flight, described state model includes some states
(E0-E16, E0 '), each state is corresponding to the possible mission phase of described aircraft, described
State model includes changing (T1-T19), and described conversion is limited between the state that these are described
Switching, it is characterised in that described state model includes at least one standard (T0-T0 '),
At least one standard described (T0-T0 ') for the initialization of described state model, described initially
Change standard (T0, T0 ') is corresponding to the original state (E0, E0 ') of described state model, often
Individual conversion and each initialization standard depend on can recording during the flight of described aircraft
At least one characteristic parameter；
Described method the most in turn comprises the following steps:
-from the flying quality of record, extract the flight number of characteristic parameter about described aircraft
According to (20)；
-calculate initialization standard according to the flying quality of the characteristic parameter about described aircraft
(30), in order to detect described flying quality and start the original state of corresponding described state model
Initial time；
-counted according to the flying quality about the characteristic parameter recorded before described initial time
Calculate multiple conversions (40) of described state model, in order to detect the feature about described aircraft
The flying quality of parameter starts the moment that the state of corresponding described state model changes；
-intercept described flying quality (50) according to the moment thereby determined that, in order to by record
Flying quality mates with mission phase.
Method the most according to claim 1, the calculating of wherein said conversion is included in described
The calculating of the conversion of at least one described state model after the detection of original state, its be given from
Described original state forwards the shape probability of state by title current state corresponding to mission phase to.
3., according to the method described in previous claim, the calculating of wherein said conversion includes at least
The calculating of one conversion, it provides the shape forwarding be later than described current state from described current state to
Probability of state.
4., according to a described method in aforementioned claim, wherein determine two conversions
Between time interval, in order to determine the state of the corresponding described state model of described flying quality
Duration.
5. according to a described method in aforementioned claim, wherein said state model
Original state is the aircraft cruised or the aircraft at the end of being in flight.
6., according to a described method in aforementioned claim, the calculating wherein changed includes
Judgement mark is calculated according to the flying quality of at least one characteristic parameter about described aircraft
Accurate.
7., according to a described method in aforementioned claim, wherein eliminate and fly described
Row data start the described flying quality before the moment of corresponding original state.
8., according to a described method in aforementioned claim, wherein said characteristic parameter is:
Normal acceleration, horizontal acceleration, longitudinal acceleration, highly, the configuration of aileron, vertically speed
Degree and horizontal velocity, pressure altitude, radar altitude, the state of undercarriage, course.
9. according to a described method in aforementioned claim, wherein said state model
State is: flight terminates, engine start, skid off, take off, refuse to take off, the second link,
Initial rise, rise, decline, cruise, march into the arena, go around, final approach, land, contact to earth
Go around, slip into.
10. for analyzing a system for flying quality, including processing unit and memory cell,
Described processing unit be applicable to application according to the method for aforementioned claim, described in deposit
Storage unit is used for storing state model.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR1253082A FR2989186B1 (en) | 2012-04-04 | 2012-04-04 | METHOD FOR ANALYZING FLIGHT DATA RECORDED BY AN AIRCRAFT FOR FLOWING IN PHASES OF FLIGHT |
| FR1253082 | 2012-04-04 | ||
| US201261642359P | 2012-05-03 | 2012-05-03 | |
| US61/642,359 | 2012-05-03 | ||
| PCT/EP2013/057102 WO2013150097A1 (en) | 2012-04-04 | 2013-04-04 | A method for analyzing flight data recorded by an aircraft in order to cut them up into flight phases |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104246637A CN104246637A (en) | 2014-12-24 |
| CN104246637B true CN104246637B (en) | 2016-08-24 |
Family
ID=46634265
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380018475.7A Active CN104246637B (en) | 2012-04-04 | 2013-04-04 | Analyze the flying quality of aircraft record with the method being truncated to mission phase |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US20150331975A1 (en) |
| EP (1) | EP2834717A1 (en) |
| CN (1) | CN104246637B (en) |
| CA (1) | CA2868922A1 (en) |
| FR (1) | FR2989186B1 (en) |
| IN (1) | IN2014DN08698A (en) |
| RU (1) | RU2627257C2 (en) |
| WO (1) | WO2013150097A1 (en) |
Families Citing this family (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3050351B1 (en) * | 2016-04-15 | 2018-05-11 | Thales | AIRCRAFT AVIONICS INTEGRITY MONITORING METHOD, APPARATUS AND COMPUTER PROGRAM PRODUCT THEREOF |
| CN107436154A (en) * | 2017-08-08 | 2017-12-05 | 西安电子科技大学 | State of flight monitoring method for civil aviaton's airborne communication |
| CN108694497A (en) * | 2018-04-13 | 2018-10-23 | 深圳市科信南方信息技术有限公司 | Flight quality data monitoring method and monitoring device |
| US11299288B2 (en) | 2019-03-20 | 2022-04-12 | City University Of Hong Kong | Method of presenting flight data of an aircraft and a graphical user interface for use with the same |
| US11164467B2 (en) | 2019-07-31 | 2021-11-02 | Rosemount Aerospace Inc. | Method for post-flight diagnosis of aircraft landing process |
| CN110674216B (en) * | 2019-09-18 | 2022-03-22 | 安徽华明航空电子系统有限公司 | Data modeling and information extraction method for flight route |
| CN110979728A (en) * | 2019-11-14 | 2020-04-10 | 深圳市瑞达飞行科技有限公司 | Flight data processing method, flight data reading method, flight data processing device, electronic equipment and storage medium |
| CN110766180B (en) * | 2019-11-21 | 2023-04-07 | 中国民航信息网络股份有限公司 | State detection method, device and system |
| CN111062092B (en) * | 2019-12-25 | 2023-11-03 | 中国人民解放军陆军航空兵学院陆军航空兵研究所 | Helicopter flight spectrum compiling method and device |
| FR3111200B1 (en) | 2020-06-08 | 2022-07-08 | Airbus Helicopters | Method and system for controlling a level of damage to at least one aircraft part, associated aircraft. |
| CN113110585B (en) * | 2021-04-28 | 2022-12-13 | 一飞(海南)科技有限公司 | Method and system for flying formation dance step state switching, unmanned aerial vehicle and application |
| CN114200962B (en) * | 2022-02-15 | 2022-05-17 | 四川腾盾科技有限公司 | Unmanned aerial vehicle flight task execution condition analysis method |
| CN115293225B (en) * | 2022-06-17 | 2023-04-28 | 重庆大学 | Method and device for analyzing causes of pilot flat-floating ejector rod |
| CN115562332B (en) * | 2022-09-01 | 2023-05-16 | 北京普利永华科技发展有限公司 | Efficient processing method and system for airborne record data of unmanned aerial vehicle |
| CN116453377B (en) * | 2023-06-16 | 2023-08-15 | 商飞软件有限公司 | Method for carrying out flight phase division on airplane QAR data |
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| CN101630446A (en) * | 2009-07-21 | 2010-01-20 | 民航数据通信有限责任公司 | Method for evaluating aircraft state based on broadcast type automatic correlative monitoring data and system thereof |
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| US4943919A (en) * | 1988-10-17 | 1990-07-24 | The Boeing Company | Central maintenance computer system and fault data handling method |
| US7181478B1 (en) * | 2000-08-11 | 2007-02-20 | General Electric Company | Method and system for exporting flight data for long term storage |
| RU2179744C1 (en) * | 2001-03-15 | 2002-02-20 | Найденов Иван Николаевич | System for preparation of data for analysis of piloting results |
| US20030004764A1 (en) * | 2001-07-02 | 2003-01-02 | Niedringhaus William P. | Air carrier service evolution model and method |
| FR2914764B1 (en) * | 2007-04-06 | 2014-10-10 | Airbus France | METHOD AND DEVICE FOR DETERMINING A FAULT DIAGNOSIS OF A FUNCTIONAL UNIT IN AN ONBOARD AVIONIC SYSTEM |
| US20090251542A1 (en) * | 2008-04-07 | 2009-10-08 | Flivie, Inc. | Systems and methods for recording and emulating a flight |
| RU2411452C2 (en) * | 2009-03-26 | 2011-02-10 | Открытое акционерное общество "Российская самолетостроительная корпорация "МиГ" | Objective control system |
| RU2427802C1 (en) * | 2009-12-01 | 2011-08-27 | Курское открытое акционерное общество "Прибор" | Data registration system |
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2012
- 2012-04-04 FR FR1253082A patent/FR2989186B1/en active Active
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2013
- 2013-04-04 EP EP13715942.2A patent/EP2834717A1/en not_active Withdrawn
- 2013-04-04 RU RU2014141020A patent/RU2627257C2/en active
- 2013-04-04 CN CN201380018475.7A patent/CN104246637B/en active Active
- 2013-04-04 US US14/389,958 patent/US20150331975A1/en not_active Abandoned
- 2013-04-04 WO PCT/EP2013/057102 patent/WO2013150097A1/en active Application Filing
- 2013-04-04 CA CA2868922A patent/CA2868922A1/en not_active Abandoned
-
2014
- 2014-10-16 IN IN8698DEN2014 patent/IN2014DN08698A/en unknown
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101630446A (en) * | 2009-07-21 | 2010-01-20 | 民航数据通信有限责任公司 | Method for evaluating aircraft state based on broadcast type automatic correlative monitoring data and system thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| US20150331975A1 (en) | 2015-11-19 |
| RU2627257C2 (en) | 2017-08-04 |
| CA2868922A1 (en) | 2013-10-10 |
| CN104246637A (en) | 2014-12-24 |
| IN2014DN08698A (en) | 2015-05-22 |
| FR2989186A1 (en) | 2013-10-11 |
| RU2014141020A (en) | 2016-05-27 |
| FR2989186B1 (en) | 2014-05-02 |
| WO2013150097A1 (en) | 2013-10-10 |
| EP2834717A1 (en) | 2015-02-11 |
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